Yuzhnoye Design Bureau

Updated 8 Aug 2026

Manufacturer Ukraine Listed

53 Products

72 Years Active

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About Yuzhnoye Design Bureau

Yuzhnoye Design Bureau (officially Yuzhnoye State Design Office, named after M.K. Yangel) was established in 1954 in Dnipropetrovsk (now Dnipro), Ukraine. It became a key Soviet center for ballistic missile and space rocket development. After Ukrainian independence, Yuzhnoye pivoted to civilian space applications, collaborating with NASA, ESA, and commercial partners. Key achievements include the Zenit launch vehicle for Sea Launch, the Antares first-stage design, the Sich Earth observation satellite series, and the Cyclone-4M medium-lift rocket. In 2023 it was reorganized into a 100% state-owned joint-stock company.

Company Info

Headquarters Dnipro, Ukraine, Ukraine

Founded 1954 (72 years)

Specializations

Propulsion Systems Spacecraft & Satellites Engineering Services Testing Services

Website yuzhnoye.com ↗

Email info@yuzhnoye.com

Photos 2

Products

1 8

Working medium	Fluoroplastic (PTFE)
Thrust	0.1 mN
Specific impulse	20,000 m/s
Total impulse	200 N*s
Maximum power	20 W
Engine dimensions	90 x 21 x 32 mm
Control unit dimensions	100 x 100 x 30 mm
Propellant handling	No pressurized gases required

1 10

Propellant	Ammonia
Number of engines	2
Engine thrust	0.049 N
Total thrust impulse (hot mode)	7,000 N*s
Total thrust impulse (cold mode)	2,500 N*s
Number of firings	Up to 500
Maximum firing duration	15 minutes
Supply voltage	24 to 34 V
Max power consumption (at 28V)	375 W
Dry mass	24 kg

1 12

Vehicle class	Medium-lift
Number of stages	2
Height	42,500 mm
Body diameter	3,900 mm
Gross mass (without payload)	330 t
Payload to 200 km x 300 km, 51.6 deg	8.1 t
Stage 1 engines	2 x RD-181
Stage 1 propellant	LOX + kerosene
Stage 1 thrust (sea level)	392 tf
Stage 2 engine	Castor-30XL
Stage 2 propellant	HTPB (solid)
Stage 2 thrust (vacuum)	48.7 tf

1 4

Liftoff mass	30.5 t
Engine	RD861K
Propellants	NT + UDMH
Payload mass delivered to lunar orbit	21.3 t

1 11

Mass	20 kg or less
Payload volume	Up to 4U
Average power	80 to 200 W
Peak power	Up to 230 W
Propellant	Iodine
Propulsion thrust (per engine)	1.24 x 10^-3 N
Total impulse (per engine)	3.7 x 10^4 N*s
Number of engines	2
Angular attitude accuracy	0.5 deg
Angular stabilization accuracy	0.005 deg/s
Active lifetime	3 years

1 8

Mass	14 kg or less
Payload volume	Up to 2U
Average power	60 to 65 W
Peak power	Up to 130 W
Angular attitude accuracy	0.5 deg
Angular stabilization accuracy	0.005 deg/s
Target orbit	Circumlunar
Active lifetime	1 year

1 17

Vehicle class	Lightweight
Number of stages	3
Height	30,000 mm
Body diameter	2,250 mm
Fairing diameter	2,250 mm
Gross mass	65 t
Stage 1 engine	RD870
Stage 1 propellant	LOX + kerosene
Stage 1 thrust (sea level)	79.75 tf
Stage 2 engine	RD809K
Stage 2 propellant	LOX + kerosene
Stage 2 thrust (vacuum)	10 tf
Upper stage engine	RD840
Upper stage propellant	NT + UDMH
Upper stage thrust (vacuum)	0.04 tf
Payload to LEO (200 km, 51.6 deg)	1.5 t
Payload to SSO (700 km, 98.16 deg)	1.05 t

2 14

Vehicle class	Medium-lift
Number of stages	2
Height	39,000 mm
Body diameter	3,900 mm
Fairing diameter	4,000 mm
Launch mass (without payload)	260 t
Stage 1 engines	4 x RD870
Stage 1 propellant	LOX + kerosene
Stage 1 thrust (sea level)	318.8 tf
Stage 2 engine	RD861K
Stage 2 propellant	N2O4 + UDMH
Stage 2 thrust (vacuum)	7.916 tf
Payload to LEO (200 km, 45.1 deg)	5 t
Payload to SSO (700 km, 98.16 deg)	3.3 t

2 18

Vehicle class	Medium-lift
Number of stages	3
Height	51,000 mm
Body diameter	3,900 mm
Fairing diameter	4,000 mm
Gross mass (without payload)	332 t
Stage 1 engines	4 x RD870
Stage 1 propellant	LOX + kerosene
Stage 1 thrust (sea level)	318.8 tf
Stage 2 engine	RD872
Stage 2 propellant	LOX + kerosene
Stage 2 thrust (vacuum)	93 tf
Stage 3 engine	RD861K
Stage 3 propellant	NT + UDMH
Stage 3 thrust (vacuum)	7.916 tf
Payload to LEO (200 km, 45.1 deg)	9.875 t
Payload to SSO (700 km, 98.16 deg)	4.86 t
Payload to GTO (Hp=190, Ha=35786 km, i=45 deg)	2.02 t

TRL 7 · Demonstrated

1 8

Propellants	NT + UDMH
Vacuum thrust	0.45 tf
Specific impulse (vacuum)	322.5 s
Propellant mixture ratio	2.25
Number of starts	10
Total mass	165.4 kg
Feed system	Pneumatic pump
TRL	7

1 6

Payload capacity (per site visit)	50 kg
Single-site maximum payload	150 kg
Number of surface sites	Up to 3
Maximum distance between sites	~20 km
Propulsion engine	RD840
Propellants	NT + UDMH

1 7

Working medium	Air, nitrogen, or argon
Maximum bottle pressure (at 20 deg C)	23 MPa
Nominal gas pressure	0.3 MPa
Total thrust impulse	250 to 7,000 N*s
Engine thrust options	0.1; 0.2; 8.5 to 55 N
Thrust excursion	+/-25%
Specific impulse	710 m/s

1 16

Satellite mass (lift-off)	4,920 kg
Payload mass	350 kg
Orbital type	Geostationary
Orbital altitude	35,786 km
Orbital inclination	0 deg
Revolution period	1,436.07 min
Position-keeping accuracy	+/-0.1 deg latitude/longitude
Attitude control	3-axis active
Attitude sensors	Astromeasuring system, angular velocity meters
Attitude actuators	Reaction wheels, electrojet engines
Orientation accuracy	0.01 deg or less
Uplink frequency	13,240 to 13,250 MHz
Downlink frequency	10,945 to 10,950 MHz
Power supply (daily average)	7,200 W minimum
Payload power allocation	6,000 W minimum
Design lifespan	15 years

1 9

Working medium	HAN-based monopropellant
Pressurant	Isobutane
Total thrust impulse	0.32 kN*s
Thrust	0.153 N
Monopropellant mass	0.15 kg
Power consumption	up to 13 W*h
Active period	at least 1.0 year
Total mass	1.1 kg or less
Dimensions	100 x 100 x 135 mm

1 10

Dimensions	111 x 110 x 370 mm
Bus mass	2,987 g
Propulsion unit mass	1,000 g
Orbit type	Near-circular
Orbital altitude	350 to 800 km
Orbital inclination	48 to 98 deg
Propulsion type	Green monopropellant
Total burn capacity	320 N*s
Attitude accuracy	+/-10 deg
Active lifetime	more than 1 year

1 7

Working medium	Xenon
Maximum bottle pressure (at 50 deg C)	13 MPa
Total thrust impulse	50 to 1,000 kN*s
Hall engine thrust	1 to 66 mN
Thrust excursion	15%
Specific impulse	2,200 to 22,000 m/s
Thrust-to-power ratio	16 to 20 W/mN

1 2

Payload capacity to lunar surface	Up to 10 tonnes
Primary applications	Lunar base modules, manned vehicles

1 4

Payload capacity to lunar surface	50 kg
Propulsion engine	RD840
Propellants	NT + UDMH
Surface operational duration	14+ days

Flight-proven

4 10

Thrust range	30 to 100 N
Propellants	Nitrogen Tetroxide + UDMH
Cyclone-4 specific impulse	2,000 m/s
Cyclone-3 specific impulse	2,600 m/s
Cyclone-4 guaranteed ignitions	30,000
Okean-o guaranteed ignitions	50,000
Cyclone-4 total run time	5,600 s
Okean-o total run time	3,600 s
Cyclone-4 thruster mass	1.16 kg
Supply voltage	28 V

1 4

Liftoff mass	92.6 t
Engines	2 x RD809K
Propellants	LOX + kerosene
Payload to translunar trajectory	30.5 t

1 5

Power output (lunar day, typical mode)	10 kW
Power output (lunar night, sleep mode)	1 to 2 kW
Solar panel area	100 m2
Total system mass	4,110 kg
Energy storage	Lithium-ion batteries + electrochemical generators

1 15

Vehicle class	Heavy-lift
Number of stages	2
Height	65,000 mm
Body diameter	3,900 mm
Fairing diameter	4,200 mm
Gross mass (no payload)	526 t
Stage 1 propellant	LOX + kerosene
Stage 2 propellant	LOX + kerosene
Stage 1 engines	3 x RD815
Stage 2 engine	RD872
Stage 1 thrust (sea level)	753.96 tf
Stage 2 thrust (vacuum)	93 tf
Payload to LEO (200 km, 51.6 deg)	18.2 t
Payload to GTO (190-35786 km)	4.52 t
Payload to lunar trajectory (with booster)	6.3 t

Vehicle class	Super heavy-lift
Number of stages	2
Height	75,000 mm
Body diameter	3,900 mm
Fairing diameter	5,100 mm
Gross mass (no payload)	1,387 t
Stage 1 propellant	LOX + kerosene
Stage 2 propellant	LOX + kerosene
Booster engines	6 x RD815
Stage 1 engines	3 x RD815
Stage 2 engine	RD872
Stage 1 thrust (sea level)	2,261.88 tf
Stage 2 thrust (vacuum)	93 tf
Payload to LEO (200 km, 51.6 deg)	59.3 t
Payload to lunar trajectory (with booster)	18.7 t

Vehicle class	Super heavy-lift
Number of stages	2
Height	80,000 mm
Body diameter	3,900 mm
Fairing diameter	6,200 mm
Gross mass (no payload)	2,246 t
Stage 1 propellant	LOX + kerosene
Stage 2 propellant	LOX + kerosene
Booster engines	12 x RD815
Stage 1 engines	3 x RD815
Stage 2 engine	RD872
Stage 1 thrust (sea level)	3,769.8 tf
Stage 2 thrust (vacuum)	93 tf
Payload to LEO (200 km, 51.6 deg)	93.2 t
Payload to lunar trajectory (with booster)	30.5 t

Vehicle class	Super heavy-lift
Number of stages	2
Height	79,900 mm
Body diameter	3,900 mm
Fairing diameter	6,200 mm
Gross mass (no payload)	3,001 t
Stage 1 propellant	LOX + kerosene
Stage 2 propellant	LOX + kerosene
Booster engines	18 x RD815
Stage 1 engines	3 x RD815
Stage 2 engine	RD872
Stage 1 thrust (sea level)	5,277.72 tf
Stage 2 thrust (vacuum)	93 tf
Payload to LEO (200 km, 51.6 deg)	133 t
Payload to lunar trajectory (with booster)	40 t

1 4

Propulsion engine	RD860M
Propellants	NT + UDMH
Variants available	Expendable or reusable
Surface operational duration	14+ days

1 16

Total mass	195 kg
Payload mass	75 kg
Orbit type	Circular sun-synchronous
Orbital altitude	~668 km
Orbital inclination	~98.1 deg
Attitude control	3-axis active with 3-axis magnetometer
Orientation accuracy	5 deg or less
Scientific data storage	100 Gbytes
Wave probe frequency range	0.1 Hz to 40 kHz
RF analyzer frequency range	20 kHz to 15 MHz
Magnetometer range	+/-65,000 nT
Magnetometer resolution	0.01 nT
Propulsion system	Ammonia, 0.049 N thrust
Solar cell efficiency	21.5 to 27.5% (GaAs/Ge, InGaP/GaAs/Ge)
Battery	Li-ion, 3 A*h
Design life	3 years

1 14

Total mass	~50 kg
Payload mass	~15 kg
Orbit type	Sun-synchronous
Orbital altitude	~500 km
Off-track re-aiming capability	+/-350 km
Data link rate	320 Mbps
Orbit correction	Available
Panchromatic resolution	~1 m
Multispectral resolution (R, G, B, NIR)	~1 m
Spotlight imaging coverage	7.5 x 7.5 km
Strip imaging swath	7.5 km
Area imaging coverage	40 x 40 km
Stereo imaging coverage	20 x 40 km
Operational life	more than 5 years

TRL 4 · Development

1 8

Propellants	O2 + kerosene
Vacuum thrust	2.15 tf
Specific impulse (vacuum)	345 s
Propellant mixture ratio	2.5
Number of starts	1
Engine weight (excl. gimbal drives)	80 kg
Cycle	Staged combustion (oxidizer-rich preburner)
TRL	4

TRL 6 · Prototype

1 8

Propellants	O2 + kerosene
Vacuum thrust	10 tf
Specific impulse (vacuum)	352 s
Propellant mixture ratio	2.62
Number of starts	Up to 4
Engine weight (excl. gimbal drives)	330 kg
Cycle	Staged combustion
TRL	6

TRL 6 · Prototype

1 9

Propellants	O2 + kerosene
Vacuum thrust	9 tf
Specific impulse (vacuum)	345 s
Propellant mixture ratio	2.5
Number of chambers	4
Number of starts	1
Engine weight (excl. gimbal drives)	325 kg
Cycle	Staged combustion
TRL	6

TRL 4 · Development

1 10

Propellants	O2 + kerosene
Sea level thrust	251.3 tf
Vacuum thrust	274.5 tf
Specific impulse (sea level)	306.7 s
Specific impulse (vacuum)	335 s
Propellant mixture ratio	2.7
Number of starts	1
Engine weight (incl. mounts and gimbal actuators)	3,200 kg
Cycle	Staged combustion, dual-thrust
TRL	4

TRL 3 · Development

2 10

Propellants	O2 + kerosene
Vacuum thrust	50 tf
Specific impulse (vacuum)	355 s
Propellant mixture ratio	2.6
Number of starts (RD835)	2
Number of starts (RD835T)	1
Engine weight rd835 (excl. gimbal drives)	830 kg
Engine weight rd835t (excl. gimbal drives)	808 kg
Cycle	Staged combustion
TRL	3

1 9

Propellants	NT + UDMH
Vacuum thrust	40.7 kgf
Specific impulse (vacuum)	315 s
Propellant mixture ratio	2.05
Chamber pressure	10 kgf/cm2
Number of ignitions	100
Total operation time	2,750 s
Engine mass	4.3 kg
Feed system	Pressurized

Flight-proven TRL 9 · Flight-proven

1 7

Propellants	NT + UDMH
Vacuum thrust	0.25 tf
Specific impulse (vacuum)	315.5 s
Propellant mixture ratio	2.0
Number of starts	8 (expandable)
Engine weight (without gimbal actuators/frame)	16.5 kg
TRL	9

TRL 6 · Prototype

1 9

Propellants	NT + UDMH
Vacuum thrust (main mode)	0.5 tf
Vacuum thrust (throttled mode)	0.25 tf
Specific impulse main/throttled (vacuum)	322.5 / 316 s
Propellant mixture ratio	2.25
Number of starts	10 (depends on onboard gas capacity)
Engine weight (excl. gimbal actuators)	34 kg
Feed system	Pneumatic pump
TRL	6

TRL 6 · Prototype

1 10

Propellants	NT + UDMH
Vacuum thrust (main mode)	1 tf
Vacuum thrust (throttled mode)	0.25 tf
Specific impulse main/throttled (vacuum)	322.5 / 316 s
Propellant mixture ratio	2.25
Configuration	Two assemblies: DB-1 (stationary) + DB-2 (gimballed)
Number of starts	10 (depends on onboard gas capacity)
Engine weight (excl. gimbal actuators)	106 kg
Feed system	Pneumatic pump
TRL	6

TRL 6 · Prototype

1 10

Propellants	NT + UDMH
Vacuum thrust (main mode)	0.5 tf
Vacuum thrust (throttled mode)	0.25 tf
Specific impulse main/throttled (vacuum)	322.5 / 316 s
Propellant mixture ratio	2.25
Configuration	3 assemblies: DB-1 (stationary) + DB-2 (gimballed) + DB-3 (stationary)
Number of starts	10 (depends on onboard gas capacity)
Propulsion system mass (excl. gimbal actuators)	112 kg
Feed system	Pneumatic pump
TRL	6

TRL 8 · Qualified

1 8

Propellants	NT + UDMH
Vacuum thrust	7.916 tf
Specific impulse (vacuum)	330 s
Propellant mixture ratio	2.4
Number of starts	5
Engine weight	214 kg
Feed system	Turbopump (gas generator cycle)
TRL	8

TRL 6 · Prototype

1 10

Propellants	O2 + kerosene
Sea level thrust	79.3 tf
Vacuum thrust	89.4 tf
Specific impulse (sea level)	301.5 s
Specific impulse (vacuum)	340 s
Propellant mixture ratio	2.68
Number of starts	1
Engine weight (excl. gimbal drives)	1,420 kg
Cycle	Staged combustion, dual-thrust
TRL	6

TRL 6 · Prototype

1 8

Propellants	O2 + kerosene
Vacuum thrust	93 tf
Specific impulse (vacuum)	350.5 s
Propellant mixture ratio	2.6
Number of starts	1
Engine weight (incl. mounts and gimbal actuators)	1,530 kg
Cycle	Staged combustion, dual-thrust
TRL	6

TRL 6 · Prototype

1 10

Propellants	Liquid oxygen + kerosene
Sea level thrust	319.2 tf
Vacuum thrust	356.4 tf
Specific impulse (sea level)	303.2 s
Specific impulse (vacuum)	338.7 s
Propellant mixture ratio	2.68
Number of starts	1
Number of engines	4 x RD870
Dry weight	6,070 kg
TRL	6

4 15

Total mass	155 kg
Payload mass	35.5 kg
Orbit type	Sun-synchronous
Orbital altitude	500 to 600 km
Orbital inclination	SSO +/-0.1 deg
Local mean solar time	10:00 +/- 60 minutes
Attitude control	3-axis active
Attitude actuators	Reaction wheels, magnetic actuators
Off-axis rotation capability	+/-35 deg
Attitude accuracy (imaging mode)	0.2 deg
Attitude accuracy (standby mode)	5 deg
Spectral bands	Green (0.51-0.59 um), Red (0.61-0.68 um), NIR (0.80-0.89 um), Pan (0.51-0.90 um)
Ground resolution	~7.8 m at nadir
Swath width	~46.6 km
Operational life	3 years

Ukrainian Earth remote sensing satellite developed by Yuzhnoye Design Bureau; launched January 2022 on Falcon 9.

1 4

Type	Earth observation / remote sensing satellite
Payload	Optical imager + ionospheric monitoring instrument
Launch	January 2022, Falcon 9 Transporter-3 rideshare
Developer	Yuzhnoye Design Bureau, Dnipro, Ukraine

1 13

Total mass	~290 kg
Orbit type	Sun-synchronous
Orbital altitude	~500 km
Attitude control	3-axis active
Attitude actuators	Reaction wheels, magnetic actuators
Off-axis maneuver capability	+/-45 deg
Panchromatic resolution	0.5 m at nadir
Multispectral resolution (R, G, B, NIR)	2 m
Strip imaging coverage	10 x 1600 km
Area imaging coverage	30 x 250 km
Spotlight imaging coverage	10 x 10 km
Stereo imaging coverage	10 x 250 km
Operational life	7 years

1 14

Total mass	1,800 kg
Orbit type	Sun-synchronous (morning-evening)
Orbital altitude	450 km
Attitude control	3-axis active
Attitude actuators	Reaction wheels, magnetic actuators
Roll angle capability	+/-60 deg
Attitude accuracy	0.05 deg
SAR bands	X-band and L-band
X-band spotlight resolution	0.5 m, 2.5 x 2.5 km swath
X-band stripmap resolution	0.75 m, 7.5 km swath
Two-band stripmap resolution (X/L)	2/5 m, 15 km swath
Two-band scansar resolution	1.5/1.5 m, 100 km swath
L-band scansar resolution	1.5 m, 250 km swath
Operational life	7 years

1 3

Vehicle class supported	Light-class
Maximum mission duration	20 days
Maximum flight time to launch point	5 hours

1 5

Application	Meteorological rockets to 100 km altitude
Vehicle configuration	6x2 or 6x4 wheeled
Diesel engine power	250 to 400 kW
Emission standard	Euro 5
Cruising range	900 km

1 6

Vehicle class supported	Medium-class
Annual launch capacity	12 launches/year
Maximum mission duration (excl. transit)	25 days
Operational temperature range	10 to 35 deg C
Maximum wave height at launch	2.5 m
Maximum wind speed at launch	10 m/s

1 8

Annual launch capacity	12 launches/year
Maximum mission duration	25 days
Max prelaunch/launch operations	3 days
Sc processing air temperature	+18 to +25 deg C
Sc processing relative humidity	Up to 80%
Sc processing cleanliness class	ISO Class 8
Ambient temperature range	-50 to +50 deg C
Max wind speed at launch (10m altitude)	15 m/s (gusts to 21 m/s)

6 11

2 12

1 15

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Main slv engine propellant	Composite, high-energy
Main slv engine max diameter	Up to 2,000 mm
Main slv engine max thrust	Up to 150 tf
Main slv engine casing	Carbon fiber-reinforced plastic (cocoon type)
Main slv engine nozzle	Swiveling control nozzle
Reboost stage engine max diameter	Up to 1,250 mm
Reboost stage engine max thrust	Up to 10 tf
Pulsed control srm operating time	0.045 to 0.05 s
Pulsed control srm max thrust	Up to 500 kgf
Launch-boost srm max thrust	Up to 8,000 kgf
Spacecraft deployment srm swivel angle	up to +/-60 degrees

Bus mass	30 kg
Maximum payload mass	Up to 20 kg
Orbital altitude range	450 to 1,000 km
Orbital inclination range	0 to 180 deg
Maximum payload power	80 W
Daily average payload power	20 W
Data transmission rate	50 Mbit/s (X-band)
Tilting range	+/-35 deg
Orientation accuracy	0.2 deg
Stabilization accuracy	0.01 deg/s
Orientation determination accuracy	0.1 deg
Active lifespan	2 years

Total mass	38.4 kg
Orbit type	Circular sun-synchronous
Orbital altitude	~705 km
Orbital inclination	~98.1 deg
Attitude control	3-axis active (magnetorquers + reaction wheels)
Orientation accuracy	0.2 deg
Payload power (max)	80 W
Payload power (daily average)	20 W
Scanpol spectral bands	370, 410, 555, 865, 1380, 1610 nm
Scanpol nadir resolution	~6 km
Msip spectral bands	410, 555, 865, 1380 nm
Msip pixel size	500 m
Msip spatial resolution	~3 km nadir
Msip field of view	60 x 60 deg
Design life	2 years

Yuzhnoye Design Bureau

About Yuzhnoye Design Bureau

Photos 2

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